The current project consists on the design of a simplified commercial aircraft wing made of carbon fiber material. A real commercial aircraft is used as a model in order to create a wing model by using finite element modelling techniques through the use of ABAQUS software. The development of the wing model involves the creation of each of the structural members of the wing, the joint of them in order to create the final model, the creation of the mesh necessary for the analysis and the application of the loads to perform an analysis that accurately predicts the stresses and displacement that the wing withstands. Two different models are presented, one consisting on one tapered section wing and the second consisting on a wing with two tapered sections. These models are subjected to two different wing loads in cruise conditions, a simplified triangular load and a load that represents a real distribution of aerodynamic loads in the wing. In order to create the final wing model made of carbon fiber material, the wing is analyzed first by using the two different geometries presented and aluminum material. The wing model evolves from the one tapered section wing under triangular loads using aluminum material to the second model under real distribution loads using carbon fiber material. The models have been optimized to decrease the weight as much as possible by taking into account the design restrictions imposed. Then, the first wing model created is a simple tapered section wing made of aluminum and subjected to a triangular distribution, and it has a mass of 8749.52 kg, while the last wing model is formed by two tapered sections made of carbon fiber material and subjected to a real aerodynamic load, and it has a mass of 4765.44 kg, which is about 45 percent lower than the first created model.